Multi-point staging strategy for low emission and stable combustion

Inactive Publication Date: 2005-06-16
UNITED TECH CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Benefits of technology

[0004] Accordingly, it is an object of the present invention to provide a

Problems solved by technology

One of the biggest challenges for gas turbines, especially for industrial applications, is to have good emission performance and combustion stability for a wide range of power settings and ambient condition.
The quenching effect creates excessive CO and UHC and high dynamic pressure.
The other issue associated with too lean fuel/air mixture is that it creates unstable combustion.
If one has

Method used

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  • Multi-point staging strategy for low emission and stable combustion
  • Multi-point staging strategy for low emission and stable combustion
  • Multi-point staging strategy for low emission and stable combustion

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[0017] Referring now to the drawings, FIG. 1 illustrates a first embodiment of a multi-point injector 10 in accordance with the present invention. The multi-point injector 10 has nozzles 12 for injecting a fuel-air mixture into a combustor stage of a gas turbine engine. The nozzles 12 are arranged in a plurality of arrays. In the embodiment of FIG. 1, the nozzles 12 are arranged in four concentric rings 14, 16, 18, and 20 with an optional nozzle in the center. While the nozzle arrays have been shown to be concentric rings, it should be recognized that the nozzles 12 can be arranged in different configurations, including but not limited to squares, rectangles, hexagons, or parallel lines.

[0018] In accordance with the present invention, means for independently controlling the fuel flow rate for each of the rings 14, 16, 18, and 20 and the optional center nozzle are provided. The fuel flow rate controlling means comprises a different fuel circuit 22 for each ring 14, 16, 18, and 20 a...

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Abstract

The present invention relates to an improved multi-point injector for use in a gas turbine engine or other types of combustors. The multi-point fuel injector has a plurality of nozzles arranged in at least two arrays such as concentric rings. The injector further has different fuel circuits for independently controlling the fuel flow rate for the nozzles in each of the arrays. Each of the nozzles include a fluid channel and one or more swirler vanes in the fluid channel for creating a swirling flow within the fluid channel. A method for injecting a fuel/air mixture into a combustor stage of a gas turbine engine is also described. At least one zone has a flame hot enough to stabilize the entire combustor flame.

Description

CROSS-REFERENCED TO RELATED APPLICATION(S) [0001] This application is a continuation application of U.S. patent application Ser. No. 10 / 260,311, filed Sep. 27, 2002, entitled MULTI-POINT STAGING STRATEGY FOR LOW EMISSIONG AND STABLE COMBUSTION, by Alexander G. Chen et al.BACKGROUND OF THE INVENTION [0002] The present invention relates to a multi-point fuel injector for use in a combustor of a gas turbine engine or other types of combustors. [0003] One of the biggest challenges for gas turbines, especially for industrial applications, is to have good emission performance and combustion stability for a wide range of power settings and ambient condition. If one has an industrial gas turbine with low emissions of NOx, CO and UHC at 100% power, as one reduces the power, which is usually done by reducing the amount of fuel to the engine, the fuel / air mixture in the combustor typically gets leaner. The leaner mixture of fuel / air lowers the flame temperature and creates a flame which can be...

Claims

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Application Information

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IPC IPC(8): F23N1/00F23R3/28F23R3/34
CPCF23C2201/20F23D2900/14021F23N1/002F23N2025/08F23R3/346F23N2041/20F23R3/286F23R3/343F23N2037/02F23N2225/08F23N2237/02F23N2241/20
Inventor CHEN, ALEXANDER G.KENDRICK, DONALD W.
Owner UNITED TECH CORP
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